TURBOMACHINE COMBUSTION CHAMBER WALL WITH SINGLE ANNULAR HOLES SET FOR INLET OF PRIMARY AND MIXING AIR Russian patent published in 2014 - IPC F23R3/06 

FIELD: engines and pumps.

SUBSTANCE: annular combustion chamber (10) of turbomachine, such as aircraft turbo-jet or turboprop engine, contains coaxial walls (14, 16) in the form of rotation bodies located one inside the other with holes (66) for primary air inlet and holes (66) for mixing air inlet into the chamber. Holes for primary air inlet and holes for mixing air inlet of each wall are actually aligned with each other along the chamber longitudinal axis (34) and form a single annular set of holes (66). The chamber contains the chamber bottom (18) wall joining inlet edges of its walls (14, 16) in the form of rotation bodies and containing holes (30), in which fuel injection systems (36) and deflectors (70) are installed. The distance (L) between annular set of holes (66) and the deflector measured along the hole axis (38) is in essence equal to half of height (H) of combustion primary zone in the chamber.

EFFECT: reducing release of nitrogen oxides from turbomachine combustion chamber using simple, effective and economic method.

12 cl, 7 dwg